The Disturbed Flapping Motion of Helicopter Rotor Blades

摘要: The article deals with the flapping motion of a helicopter blade when disturbed by external forces (gust, variation in cyclic pitch). investigation is based on rectangular and untwisted hinge rotor axis. disturbance gives rise to nonperiodic oscillations, which are described linear differential equation periodic coefficients. In solving this equation, criterion obtained permits rapid determination conditions stability. Numerical evaluation shows that stable, though at certain critical advance ratio partial destabilization sets increases increasing flying speed. influence coupling between angle pitch also considered. Practically, finished after one revolution rotor.